Low-impact landing system for rotary wing aircraft

Abstract

The invention is a low-impact landing system for a rotary wing aircraft comprising a landing pad 110 having a landing surface 111 for landing the rotary wing aircraft 10, an inclination drive unit 120 on the landing pad 110 to support the landing pad 110 and adjust the horizontal inclination of the landing pad 110 according to a control signal, a ground communication unit 130 for receiving an airframe inclination detection signal detected by an airframe inclination detection unit 15 on the rotary wing aircraft 10, and a drive control unit 140 to control the inclination drive unit 120 according to the airframe inclination detection signal so that each landing gear 12 of the rotary wing aircraft 10 contacts the landing surface 111 of the landing pad 110 at the same timing.

1 . A low-impact landing system for a rotary wing aircraft for reducing landing impact transmitted to the aircraft airframe  11  when the rotary wing aircraft  10  lands, which comprises: a landing pad  110  having a landing surface  111  formed on the upper portion for landing the rotary wing aircraft  10 ; an inclination drive unit  120  positioned at a lower position of the landing pad  110  to support the landing pad  110  and drive according to a control signal to adjust the horizontal inclination of the landing pad  110 ; a ground communication unit  130  for receiving an airframe inclination detection signal detected by an airframe inclination detection unit  15  positioned on the rotary wing aircraft  10 ; and a drive control unit  140  that controls the inclination drive unit  120  according to the airframe inclination detection signal so that each landing gear  12  of the rotary wing aircraft  10  contacts the landing surface  111  of the landing pad  110  at the same timing. 
     
     
         2 . The low-impact landing system for a rotary wing aircraft of  claim 1 , wherein the inclination drive unit  120  includes a base plate  121  that is fixedly installed and spaced downward from a landing pad  110 , and a plurality of actuators  122  that are installed spaced apart from each other along the perimeter of the landing pad  110  and are extended vertically between the base plate  121  and the landing pad  110  to actuate the landing pad  110  up and down while performing an extension and contraction operation according to a control signal of a drive control unit  140 , and the drive control unit  140  individually controls each actuator  122  so that the landing pad  110  performs a roll operation and a tilt operation to be adjusted horizontally by the extension and contraction operation of each actuator  122  according to a received airframe inclination detection signal. 
     
     
         3 . The low-impact landing system for a rotary wing aircraft of  claim 2 , wherein the landing pad inclination detection unit  191  is further included, which is arranged on the landing pad  110  or the inclination drive unit  120  and outputs a detection signal necessary to calculate a landing pad inclination angle (θ 2 ) at which the landing pad  110  is inclining with respect to the horizontal plane, and the drive control unit  140  receives the airframe inclination detection signal of the airframe inclination detection unit  15  to calculate the airframe inclination angle (θ 1 ) at which the airframe  11  is inclining with respect to the horizontal plane, receives the detection signal of the landing pad inclination detection unit  191  to calculate the landing pad inclination angle (θ 2 ), and individually controls each actuator  122  of the inclination drive unit  120  so that the landing pad inclination angle (θ 2 ) becomes equal to the airframe inclination angle (θ 1 ). 
     
     
         4 . The low-impact landing system for a rotary wing aircraft of  claim 3 , wherein the ground communication unit  130  receives the airframe position information of the airframe  11  detected by the airframe position detection unit  17  arranged on the rotary wing aircraft  10 , and the drive control unit  140  starts controlling the inclination drive unit  120  when the rotary wing aircraft  10  approaches the landing pad  110  within a set distance according to the received airframe position information of the airframe  11 , and individually controls each actuator  122  so that the landing pad  110  should move horizontally by the extension and contraction of each actuator  122  according to the received airframe position information, and the landing gear  12  of the rotary wing aircraft  10  should land toward the center position of the landing surface  111 . 
     
     
         5 . The low-impact landing system for a rotary wing aircraft of  claim 2 , wherein the landing pad  110  has a size that is relatively larger than or corresponding to the opening  21  formed in the ground  20 , the ground communication unit  130  receives the airframe position information detected by the airframe position detection unit  17  arranged in the rotary wing aircraft  10 , and the drive control unit  140  controls the landing pad  110  arranged horizontally on the same line as the ground  20  to rise to a set height when the rotary wing aircraft  10  approaches the landing pad  110  within a set distance according to the airframe position information of the received airframe position detection unit  17 , and the horizontal inclination of the landing pad  110  is adjusted according to the airframe inclination detection signal of the airframe inclination detection unit  15  so that each landing gear  12  comes into contact with the landing surface  111  at the same timing, and when the rotary wing aircraft  10  lands on the landing pad  110 , each actuator  122  is controlled to descend so that the landing pad  110  should become horizontal and be positioned on the same line as the ground  20 . 
     
     
         6 . The low-impact landing system for a rotary wing aircraft of  claim 1 , wherein it further includes a wind detection unit  170  installed on the ground  20  spaced a certain distance from the landing pad  110  to detect the wind direction and wind speed applied toward the landing pad  110 , and the drive control unit  140  controls the inclination drive unit  120  to further incline the horizontal level of the landing pad  110  in the direction in which the airframe  11  of the rotary wing aircraft  10  is predicted to incline due to the wind according to the wind detection signal received from the wind detection unit  170 . 
     
     
         7 . The low-impact landing system for a rotary wing aircraft of  claim 1 , wherein exhaust holes  112  are formed on the landing pad  110  to discharge the air wind generated by the rotation of the propeller  13  provided on the rotary wing aircraft  10  and directed the air wind being toward the landing surface  111  to the lower part of the landing pad  110 , and an exhaust window  180  is further formed to discharge the air wind discharged downward through the exhaust holes  112  to the outside, which is arranged in the lower space of the landing pad  110 .